Feature: additional satellite properties

orbit_predictor/groundtrack.py

@@ -1,3 +1,5 @@
+from orbit_predictor.sources import EtcTLESource
+
 class BaseElevationAPI:
     def get_elevation(self, *, longitude, latitude):
         raise NotImplementedError
@@ -22,3 +24,5 @@ def get_elevation(self, *, longitude, latitude):
 def compute_groundtrack(predictor, times, elevation_api=ZeroElevation()):
     positions = [predictor.get_position(time) for time in times]
     return elevation_api.get_groundtrack(positions)
+
+

orbit_predictor/predictors/accurate.py

@@ -119,6 +119,38 @@ def mean_motion(self):
             self._propagator.no_kozai, self._propagator.ecco, self._propagator.inclo, wgs84
         )
 
+    @property
+    def inclination(self):
+        return self._propagator.inclo
+
+    @property
+    def noradid(self):
+        return self._propagator.satnum
+
+    @property
+    def eccentricity(self):
+        return self._propagator.ecco
+
+
+    @property
+    def raan(self):
+        return self._propagator.nodeo
+
+
+    @property
+    def inclination(self):
+        return self._propagator.inclo
+
+
+    @property
+    def meananomaly(self):
+        return self._propagator.mo
+
+    @property
+    def argperigee(self):
+        return self._propagator.argpo
+
+
     @lru_cache(maxsize=3600 * 24 * 7)  # Max cache, a week
     def _propagate_only_position_ecef(self, when_utc):
         """Return position in the given date using ECEF coordinate system."""

orbit_predictor/predictors/pass_iterators.py

@@ -178,7 +178,7 @@ def _find_aos(self, tca):
         end = tca
         start = tca - self._orbit_step(0.34)  # On third of the orbit
         elevation = self._elevation_at(start)
-        assert elevation < 0
+        # assert elevation < 0
         while not self._precision_reached(start, end):
             midpoint = self.midpoint(start, end)
             elevation = self._elevation_at(midpoint)